Swirl Preburner Mixing for Rocket Engine Temperature Control

Resolve Bottlenecks,
Find Innovative SolutionsGenerate Solutions

Solution Overview

Problem

Rocket engine components are temperature-sensitive and prone to failure due to high combustion temperatures, particularly in preburners where inefficient fuel and oxidizer mixing leads to wide temperature ranges, damaging downstream turbines and the preburner itself.

Innovation Solution

A swirl preburner system that introduces first and second fluids into swirl chambers, generating swirling flows which mix efficiently in a mixing chamber, with a third fluid used to dilute the combustion products, reducing temperature and extending the lifespan of temperature-sensitive components.

Engineering Contradictions & Design Principles

VSEngineering Contradiction Analysis

1Reliability

If traditional preburner mixing is used, then fuel and oxidizer can be supplied to the preburner, but inefficient mixing leads to wide temperature ranges that damage downstream turbines and the preburner itself

Engineering Contradiction:

Improvepreburner and turbine component lifespanVSAvoidcombustion temperature range

Core Design Contradiction:

ReliabilityVSTemperature

Solution Approach 1:

The preburner is divided into multiple swirl chambers (first swirl chamber, second swirl chamber) with separate fuel and oxidizer injection paths. This segmentation allows independent control of fuel and oxidizer mixing, enabling more precise combustion temperature control and reducing the temperature range that damages components.

Inventive Principle:

Principle #1Segmentation

Solution Approach 2:

The invention changes the mixing parameters by introducing swirl flow through tangential injection ports in multiple chambers. This alters the mixing dynamics to achieve more uniform combustion, reducing peak temperatures and extending component lifespan.

Inventive Principle:

Principle #35Parameter changes

2Use of energy by moving object

If preburner combustion is used to generate heat, then energy is produced, but high combustion temperatures expose temperature-sensitive elements to damaging heat

Engineering Contradiction:

Improveenergy production in preburnerVSAvoidthermal damage to temperature-sensitive components

Core Design Contradiction:

Use of energy by moving objectVSObject-affected harmful factors

Solution Approach 1:

The invention converts the harmful high-temperature combustion into beneficial controlled-temperature combustion by using multiple swirl chambers with optimized fuel-oxidizer mixing. The swirl flow promotes complete and uniform combustion, reducing peak temperatures while maintaining energy production, thus protecting downstream turbines and the preburner itself.

Inventive Principle:

Principle #22Blessing in disguise (Convert harm into benefit)

3Reliability

If connectors between preburner and turbine are made longer to allow cooling, then temperature-sensitive components are protected, but the size and mass of the rocket engine increase

Engineering Contradiction:

Improveprotection of temperature-sensitive componentsVSAvoidengine mass

Core Design Contradiction:

ReliabilityVSWeight of moving object

Solution Approach 1:

The invention performs preliminary cooling action within the preburner itself through the multiple swirl chamber design, which promotes efficient mixing and reduces combustion temperatures before the gases reach downstream components. This preliminary temperature reduction eliminates the need for long connector tubes, reducing engine mass while still protecting temperature-sensitive components.

Inventive Principle:

Principle #10Preliminary action

Applied Scientific Principles

This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.

Function Achieved in This Case

The swirl preburner system achieves improved mixing of fuels, reducing combustion temperatures to a narrower range, thereby extending the life of rocket engine components and reducing the size and mass of the engine by minimizing the length of temperature-sensitive structures.

Implementation Method 1

A first fluid can be introduced into a first swirl chamber... and can generate a first fluid flow that propagates toward a first swirl chamber second end... The first fluid flow can swirl within the first swirl chamber

Methodology Applied

Scientific EffectSwirl flow: Vortex Ring

Implementation Method 2

The first and second fluid flows can leave the first and second swirl chambers into a mixing chamber and can mix within the mixing chamber

Methodology Applied

Scientific EffectTurbulent mixing: Turbulence

Implementation Method 3

Combustion in a preburner is one source of heat that can potentially be damaging to rocket engine parts

Methodology Applied

Scientific EffectCombustion: Combustion

Data Source

PatentUS11815049B2Swirl preburner system and method

Publication Date: 2023.11.14 STRATOLAUNCH LLC

AI summary

A swirl preburner that includes a first core defining a first swirl chamber having a first swirl chamber first end and a first swirl chamber second end, the first swirl chamber comprising a first diameter at the first swirl chamber first end and a second smaller diameter at the first swirl chamber second end that is smaller than the first diameter; and a second core defining a second swirl chamber having a second swirl chamber first end and a second swirl chamber second end, the second swirl chamber comprising a third diameter at the second swirl chamber first end and a fourth smaller diameter at the second swirl chamber second end that is smaller than the third diameter, the first diameter being smaller than the third diameter and larger than the fourth smaller diameter.